Power amplifier



Sept. 23, 1941. e. BARTH POWER AMPLIFIER Filed Aug. 19, 1939 3 Sheets-Sheet 1 Sept. 23, 1941. G. BARTH POWER AMPLIFIER Filed Aug. 19, 1939 3 Sheets-Sheet 2 Sept. 23, 1941. 5mm 2,257,031

rowan AMPLIFIER Filed Aug. 19, "1939 3 Sheets-Sheet 3 INVENTOR,

ATTORNEY.

Patented Sept. 23, 1941 UNITED 'STATES PATENT OFFICE POWER AMPLIFIER Gustav Barth, Berlin, Germany, assignor to Siemens Apparate und Masohinen Gesellschatt mit beschrankter Hattung, Berlin, Germany, a

corporation of Germany Application August 19, 1939, Serial No. 290,968 In Germany August 19, 1938 6 Claims. (Cl. 171--242) tube amplifier. Each one is open to a number of objections. A relay is always either open or closed and this results in a discontinuous form 01 control which is reflected in a wobbly course and unnecessary consumption of power. Furthermore, the moving contacts of relays are inherently subject to deterioration.

A vacuum tube amplifier, to serve the purpose in hand, must have a high gain and must also appropriate to operat mechanisms for restoring l deliver an amount of controlling power substanthese equilibrium iti tially in excess of the capacity of standard power Another object is to provide an inexpensive b ss means t a a u be of o tp t translating device of this character which shall tubes must be placed in parallel and that the opbe of small weight. and not require high operatcrating voltages for the amplifier must be high. jng Voltages Aside from the fact that to obtain the necessary Other objects are to increas the efficiency and h voltages the p fi Power pp y unit gain of devices of the above type, to reduce the must e D S e d y. thevolta t e load on a sensitive deviation-responsive instru- Selves a e ous in an airplane Where q ment from which the controlling signal is deters are mp d d he ma t p i y of rived, and to eliminate from such devices vacuum sparkover s be rigorously guarded nst. tubes and relay contacts or other delicate mov- An d on l drawback which is of considering -t able importance is that the electrical parts of A further object is t provide improvedmeans the deviation-responsive instrument and all auxfor automatically balancing, guiding or steering iliary pp ra s a e i ly connected an airplane or other vehicle, and the invention through the ampl fi 80 that their e ct D will be described in detail in terms of an em- 'bentials y be of pposi e po a ty with espect bodiment particularly adapted to attaining this to the airplane yspeiflc t- In view of the above-described situation which It is well known to equip an airplane with in- Prevails in an p e, I accomplish e J' struments which are sensitive to any departure of my invention by providing all p y or deviation from a prescribed course or orientatranslating Sy e which includes a novel election and deliver small electric signals proportromagnetic device which, I term a magnetic tional to the departure. The'gyro horizon and amplifieru e by employing u novel the earth inductor compass .are familiar examcomponent units Connected in a p u a W y. ples of such instruments. But in order to hold a ple power is available t Operate the servot plangen it course it i necessary t t, motor and no power is drawn until a deviation considerable force on rudder, elevator and ailertakes p e, while the sy s a Whole is sensions. It is out of the question to derive this force fi e a minute Signal SO that t e load of the directly from the deviation-responsive instru", ationesponsive device may be ne y ment, since the instrument would thereby be so 0 Smalloverloaded that its motions would be determined More p cu y, the invention consists in the less by the deviation than by the load, which novel construction and combination of parts would render it useless. It is therefore customhereinafter. described; s ted in the accomary to interpose a servo-motor between the devi- D y d aw s nd po ted out in the claims ation-responsive instrument and the airplane eto appended; t be u derstood that varicontrol surface and to supply the motor with OHS changes in o P p io size and minor power related to the signal. Even when this is i s of construction within the scope or the done, however, some form of amplifier is essen- C ms y be resorted t0 Without departing 'tial, since it is imperative to keep the load on from the spirit or sacrificing any of the advanthe deviation-responsive instrument as low as tages of the invention.

' possible, whereas the servo-motor, particularly For a clearer comprehension of the invention in a large airplane, must draw a substantial e e e is d e d to the any g drawamount of power. ings which illustrate a preferred embodiment Th two known types of amplifier used for this thereof wherein: purpose are the relay and the standard vacuum Fig. 1 shows schematically a devic for restorthe amount oi. resoribed cours use or magnetic amplifier sys hows in detail according: my schematic di grain illus my invention in. sinip a wiring diagram illustrati es noon which my inventici the cart 6 "s a ,iring diagram illustrat n:

, oi cogs iven by another niotor 7.6. The conof e part of my toyenti signal is derived from the brushes 2!! are l1 showing the role 21 i; u connected to the input terminals of input to my amplifier the output the magnetic enniiifier 2E, and" the output terthereof; and r are connected to the Fig. 8 is a graph showing the relation between motor 2 the signal. input to my amplifier and the i: not to n la. transmission device of a type known per se the servo-motor which operates the control suris provided for the teletransmission of the brush face. position of the earth inductor to the instrument Referring now to the figures, Fig 1 shows diagrammatically an automatic stah lZillg' device the pilots seat. In this transmission system a. arranged to compensate for departures of an ol2- t'cnsmitter 2G, mechanically coupled to the plate ject about two mutually perpendicular axes from 2i, electrically connected to a receiver 23 which its equilibrium position; for example, to com in turn is mechanically coupled to an indicator pensate for the pitch and roll or an. sire-lane, dial The transmitter 26 and the receiver vessel, or vehicle about its longitudinal sins and 2 may conveniently be a pair of matched selfits transverse axis respectively. For this pursynchronous motors, supplied with alternating pose a convenient deviation-responsive device is current power through the terminals 26 and 23' an absolute vertical indicator in the form of e. in the well known manner. gyroscopic horizon. The gyroscopic horizon is The system as shown in Fig. 2 merely indicates equipped with a rotor, spinning rapidly about a to the pilot the departure of the airplane from vertical axis and suspended in gimbals in neutral a prescribed orientation in a horizontal plane, equilibrium- The y is mounted n a o g and the pilot may then operate the rudder man- I which is p v d 0 1 journals 2 to rock about a ually to restore the airplane to its course. It will transverse axis within a frame 3. The frame 3 be understood, however, that if desired, the is in turn supported by journals 4 in bearings 5, servo-motor 24 may be arranged to operate the 6 to rocl: about the longitudinal axis of the airrudder of the airplane instead of turning the plane, whose direction of travel is indicated by plate 2!, in which case the deviation itself is the arrow F. compensated instead of being merely indicated Extensions of the journals 2 and 4 are proto the pilot. vided with contactors 8 and l arranged to swing Fig. 3 shows in detail the internal connections over arcuate resistors l2 and H mounted, reof a magnetic amplifier according to my invenspectively, on the body of the plane and the outer tion which, as above stated, is indicated in Figs.

frame 3. 1 and 2 by l3, l4 and 25. In this figure four units A source of voltage H, which may conven- I, II, III, IV, are provided, each including a core, iently be a storage battery or the like, is concoils and a rectifier. The four cores 3|, 32, 33

nected to the ends of the resistor II and a similar and 34 are composed of a material having a high source of voltage I2 is connected to the ends of magnetic permeability range, that is, a permethe resistor I2. The midpoint of each battery able but saturable material; for example, they is connected to the midpoint of its associated may be composed of an iron-nickel alloy. The resistor. The input terminals of a unit l3, which cores are arranged in pairs, 3| adjoining 34 and includes amagnetic amplifier and such auxiliary 32 adjoining 33, so that they are closely couapparatus as may be necessary, are connected to 'pled. If desired, each pair may be replaced by the midpoint of the battery H and to the mova single three leg core. Four coils 35, 36, 31 and able contactor I; and another magnet. amplifier 38 are wound upon the cores as shown and a unit i4 is similarly connected to the battery l2 rectifier is connected in series with each of these and the contactor 8. windings. These rectifiers 4|, 42, 43 and 44 are The output terminals of the units l3 and [4 preferably full-wave copper-oxide rectiflers 0! supply currents to the servo-motors 9 and I0 well known type although rectifiers of any derespectively which, through mechanical linkages sired tvpe will serve.

9 and i3 operate the control surfaces of the It W111 be observed by tracing the connections airplane. Additional terminals l3 and M of of Fig. 3 that the winding 35 and the rectifier 4| the magnet amplifiers l3 and M- will be more are connected in series with the winding 36 fully described hereinafter. It should be 'oband the rectifier 42 across a source of alternatserved at this point, however, that the power ing voltage 43, which may be any convenient required to drive the motors 8 and HE is derived low-voltage A. C. generator; Similarly, the windfrorr these terminals l3 and 4, the input tering 31 and the rectifier 43 are connected in series minals of the magnet amplifiers receiving only with the winding 38 and the rectifier 44 across minute signals from the potentiometers ii and the same source 49, but in the opposite sense. l2. It will be noted further that the only load The coils 35 and 38-are wound upon the same on the gyro horizon is the frictional resistance composite core ill-34 and the windings 3B and of thecontactors l and 8 on the resistors H and 31 on the other composite core 32-33; and the panel of the airplane, conveniently located near coils are wound in such direction that voltage at the terminals 49 will produce, due to the winding 35, flux in the sam circular direction as the flux produced in the same core due to the winding 38 by the same voltage at the terminals 49. Thus the fluxes in the core 3|-34, due to the windings 35 and 38, are aiding fluxes so that the windings 35 and 38 constitute high inductive impedances.

The same considerations apply to the core 32-33 and the windings 36 and 31 so that these windings likewise constitute high inductive impedances.

It will be observed that the connections of Fig. 3 are such thatthe coils 35, 36, 31 and 33, with their associated rectifiers 4|, 42, 43, and 44 constitute the four arms of a Wheatstone bridge. This arrangement is more clearly indicated in Fig. 4, where many connections have been omitted for the sake of clarity.' In this bridge, however, the arm 35 is inductively coupled to the diagonally opposite arm 38 and the arm 35 is inductively coupled to the diagonally opposite arm 31.

This bridge is supplied with voltage from the alternating current terminals 49 and the midpoints of the bridge, indicated at a and b in Fig. 4, are connected to a phase-sensitive device 50 which will be more fully described below.

A coil 39 is wound about the central leg of the composite core 3|34 and a similar coil is wound about the central leg of the composite core 32-33. These coils are Wound in the same direction and placed in series with terminals 52 which carry the signal current.

Auxiliary coils 45 and 48 are similarly wound about the central leg of the composite core 3 |-34, and are connected to the output terminals of the rectifiers 44 and 4|, respectively. Similarly, auxiliary coils 46 and 41 are wound on the central leg of the composite core 32-33 and connected respectively to the output terminals of the rectifiers 43 and 42.

A condenseris connected across the input terminals of each rectifier in the well-known manner, to reduce the alternating current impedance of the rectifiers.

Fig. 5 shows some of the connections of one unit of Fig. 3 in simplified form and serves to explain the operation of the magnet amplifier. In Fig. 5, 3| again denotes the core of a permeable but saturable material. 35 indicates a coil which in Fig. 3 forms the bridge arm of the unit I and to which current is supplied from a source of alternating current 5|. Another coil 39 is wound about the same core and corresponds generally with any of the windings 39, 45 and 48.

If an alternating current voltage is impressed at the terminals 5| a current Y will flow through the winding 35. The magnitude of this current is determined in large measure by the inductance of the coil 35 which in turn depends upon the permeability of the core 3|. If a direct current i be supplied to the terminals 52, the operating point of the core material on its B-H characteristic will be moved, and the permeability of the core 3| will in general be decreased so that the current Y increases.

The alternating current impedance of the coil 35 is consequently a function of the direct current i in the coil 39 so that the magnitude of the current Y can be varied by controlling the magnitude of the direct current i.

Fig. 6 shows, in addition to the core and windings of Fig. 5, a rectifier 4|, its input terminals rectifier 4|. When the direct current i flowing in i the winding 39 is zero, the alternating current Y flowing in the winding 35 is limited largely by the impedance of that winding. Through the coil '45 there flows a direct current 1 derived from the rectifier 4| and related in magnitude to the alternating current Y. This current 11 partly saturates the core 3|, thereby changingthe permeability of the core 3| and consequently the impedance of the winding 35 from the value it would otherwise have, exactly as explained above in connection with the effect of the current i in the coil 39 of Fig. 5.

If now, in addition, a current i be caused to flow through the winding 39 the saturation of the core 3| will either be increased or decreased depending on the direction of the winding 39 and the sense of the current i. In other words, the fiux due to the current i either adds to or subtracts from the flux due to the current If the effect is additive, the current Y will increase and so increase the current y.- This will in turn increase the saturation of the core 3| and further reduce the impedance of the winding 35 so that the current Y will increase still further. Thus the action is cumulative giving rise to a large' change in Y for a small change in i.

If, however, the sense of the current i is such that the action is subtractive, there results partial or complete mutual neutralization of these effects depending upon the magnitude of the current 2'. Thus the current imay be adjusted to exactly neutralize the flux due to the current 1 giving rise to a maximum of the impedance of the winding 35 corresponding to a certain small value-of the current i; and an increaseof the current 2' in the same sense will more than neutralize the flux due to the current 1! so that the current Y again increases.

These relations are shown graphically in Fig. 7 in which the minimum value of Y corresponds to a certain low value of i which is negative with re.- spect to y; and Y0 is the value which the current Y obtains when the current i is zero, due

to partial saturation of the core 3| by the current 1 alone.

Returning now to Fig. 3, advantage is taken of both of these phenomena, namely, the regenerative action when the fluxes are cumulative and the degenerative action when they are subtractive. The windings 39 and 40 are traversed by the input signal current derived from the deviation-responsive device; and this current, ie, which corresponds to the current i of Figs. 5 and 6 may be positive, negative or zero. The rectifiers 4|, 42, 43 and 44 and their associated windings 45, 4B, 41 and 48 operate in the manner described in connection with Fig. 6 toproduce increase or decrease'of the flux compared with the values the flux would have due to the current is in the windings 39 and 40 alone.

It is important to note that the direction of the winding 45, 46, 41 and 48 with respect to the windings 39 and 40 is such that a given signal current ie will act oppositely on the two composite cores; for example, it will reduce the permeability of the core 3|34 and therefore the impedance of the coils 35 and 38 together, and at the same time it will increase the permeability of the core 3233 and therefore the impedances of coils 36 and 31 together. But although magnetically coupled, the coils 35 and 38 constitute diagonally ,op-

posite arms of the Wheatstone bridge and likewise the coils 35 and 3! constitute the other two diagonally opposite arms of the same bridge. This arrangement, which is more clearly shown in Fig. 4, results in substantially doubling the sensitivity of the device over what it would be if the impedances 31 and 38, for example, were constant and only the impedances 35 and 36 varied by the current i5.

A further advantage in the arrangement of my invention lies in the fact that since the coils 45, 46, 41 and 48 always link two cores a defect which would reside in the simpler arrangement of Figs. 5 and 6 is eliminated. In Fig. 5, the coils 35 and 39 are inductively coupled in such a way that undesirable electromotive forces would be induced in the coil 39 by change of the current Y in the winding 35. The same is true of the arrangement of Fig. 6 in which undesirable electromotive forces would be induced in the coils 39 and 45 by change of current Y in the coil 35. In the arrangement of Fig. 3, on the other hand, the directions of the windings 35 and 38 or 36 and 3'! are such that the electromotive forces induced in the windings 39, 45 and or 40, 46, and 41 by the currents flowing in the first mentioned windings will neutralize one another so that the above mentioned undesirable .reaction cannot occur.

It will now be understood that when an alterhating voltage is supplied to the terminals 49, and the signal current ie is zero, which corresponds to the airplane equipped with the apparatus of Fig. 1 following its true path without pitch or roll, the bridge of Fig. 3 is balanced, all the impedances 35, 36, 31 and 38 being equally high. Therefore, the voltage across the midpoints a, b, of the bridge, is zero. If, however, the airplane departs from its prescribed orientation, the deviationresponsive device will deliver a signal current, positive or negative, to the coils 39 and 4a, which will increase the saturation of one pair of cores and decrease the saturation of the other pair. The bridge will then be doubly unbalanced and a substantial voltage will appear at the points a, b.

If now the signal current ie should reverse its direction due to a change in the sense of the deviation of the airplane from its preassigned course, units II and III will interchange their roles with units I and IV so that if, for example, units I and IV at first operated cumulatively and units II and III differentially, units :1 and IV will now operate diiferentially and units II and III cumulatively. When the bridge is unbalanced in one direction the voltage impressed on the points a, b, is in a certain. phase; and when the bridge is unbalanced in the opposite direction this voltage is in opposite phase. As the signal current ie passes through its zero value the voltage at the points a, b, decreases, passes through zero, and increases again in opposite phase.

The midpoints a, b of the bridge are connected to the input terminals of a phase-sensitive device 50. This device is of the sort which responds to the variation of an alternating voltage or current both in magnitude and in phase. It is supplied at the points c, d, with a reference voltage or current of standard magnitude and phase which is preferably derived from the source 49. Utilizing the same source for these two purposes ensures that their frequencies shall be identical. As shown, the terminals 0, d are directly connected to the terminals 49 with the interposition of a phase advancer 53.

It is the function of the phase-sensitive device 50 to supply to the ultimate receiver, for example any one of the servo-motors 9, III, or 24, a direct current Ja which is substantially proportional to the magniture of the alternating current input to the device 50 but which changes its sign when the alternating current input undergoes a phase reversal. This result may be attained by the use of circuit arrangements which make the current Ja proportional to the magnitude of the alternating current input to the terminals a, b and also to the cosine of the phase angle between this voltage and the standard voltage on the terminals 0, d.

The phase advancer 53, which may be of any desired type, is interposed between the source 43 and the terminals 0, d, to advance or retard the phase of the standard voltage by a preassigned amount in order that the cosine shall change from positive to negative, and so change the sign of the output current Ja, when the signal current is is zero. The phase rotation inthe phase advancer 53 may be preset or may be controllable at the will of the operator. Indeed, control of the phase rotation within the device 53 constitutes a convenient means of controlling the amplification and therefore the sensitivity of the translating device as a whole. The performance of the phase-sensitive device 50 is represented in Fig. 8. As above stated, the magnitude of the output direct current Ja is proportional to the magnitude of the bridge current; but it changes its sign and becomes negative when the bridge current passes through a phase reversal. It is therefore substantially proportional both in magnitude and sign to the input signal current ie, so that the servo-motor will, finally, operate the control surfaces of the airplane in proportion to the deviation.

The phase-sensitive device may be a mechanical rectifier, a dry rectifier bridge connection, a tube rectifier, a fork modulator, a ring modulator, or any other type of modulator, connected either singly or in push-pull.

I have found that the sensitivity and gain of the system according to my invention are adequate to operate the servo-motors which move the control surfaces of an airplane and that it iseasily actuated by the small signal currents delivered by a gyro horizon or an earth inductor Without overloading the latter. Its efficiency is many times that oi a tube amplifier. It may be of compact, rugged, and inexpensive construction and of low weight. Both the required source voltages and the induced voltages are low so that the danger of accident is substantially eliminated. Lastly, the only coupling between the signal source and the remainder of the apparatus is inductive, and there is no direct electric connection at all.

In the arrangement above described the signals actuating my translating device have been proportional to the departure or deviation of the airplane from a preassigned position or course. It will be understood that my invention is equally-adapted to receive and translate signals derived from the velocity or acceleration of such deviation in the well known manner.

Though, for the sake of clearer illustrations, I have described the invention in connection with a device for indicating or compensating for deviation of a vehicle from a position orcourse, it will be understood that it may have a large number of entirely different uses. Indeed, I apprehend that it may be useful in any field wh r the second core, a phase shifting device conit is desired to translate a minute electric signal second winding for the first core, a second wind- H ing for the second core, rectifying means for' each of said second windings and connecting said second windings in series opposed relation to said first windings for energization by said .alternating current source, a direct current input circuit including a third winding on the first core and a third winding on the second core, the

third winding of one core being connected in aiding relation with the third winding of the other core, a first pair of auxiliary windings on said first core and connected to the output of the rectifying means of the first and second winds of the first core, whereby direct current flows in said pair of auxiliary windings in accordance with the alternating current in said first and second windings of the first core, a sec.-

ond pair of auxiliary windings on said second" core and connected to the output of the rectify- I ing means of the first and second windings of the second core whereby direct current flows 1n said second pair of auxiliary windings in accordancewith thealternating current in said first and second windings of the second core, the first pair of auxiliary windings of the first core being wound in opposed relation to the second pair of windings of the second core, and means electrically connected to the output of the first and second windings of the two cores and to said alternating current source.

2. A magnetic amplifier compnsmg a first magnetizable core carrying a first winding, a second magnetizable core carrying a first winding, an alternating current source for energizing said windings, rectifying means for each of said windings and connecting said windings in series,

a second winding for the first core, a. second windingfor the second core, rectifying means for each of said second windings and connecting said second windings in series opposed relation to said first windings for energization by said alternating current source, a direct current input circuit including a third winding on thefirst core and a. third winding on the second core, the

third winding of one core being connected in aiding relation with the third winding of the other core, a first pair of auxiliary windings on said first core and connected to the output of the rectifying means of the first and second windings of the first core whereby direct current .flows in said pair of auxiliary windings in accordance posed relation to the second pair of windings of nected to said alternating current source, and means electrically connected to said phase shifting device and to the output of the first and sec ond windings of the two cores.

3. A magnetic amplifier comprising a first magnetizable core carrying a first winding, a second magnetizable core carrying a first winding, an alternating current source for energizing said windings, rectifying means for each of said windings and connecting said windings in series, a second winding for the first core, a second "winding for the second core, rectifying means for each of said second windings and connecting said second windings in series opposed relation to said first windings for energization by said alternating current source, a direct current inputcircuit including means carried by each of said cores and connected in aiding relation, a first auxiliary winding on the first core connected to the output of the rectifying means of the first winding of the first core whereby direct current flows therethrough, a second auxiliary winding on the first core connected with the output of the rectifying means of the second winding of the first core whereby direct current fiows therethrough, a first auxiliary winding on the second core connected with the output of the rectifying means of the first winding of the second core whereby direct current flows therethrough, a second auxiliary winding on the second core connected with the output of the rectifying means of the second winding of the second core whereby direct current fiows therethrough, said first and second auxiliary windings of the first core being wound in opposed relation to the first and second auxiliary windings of the second core, and means electrically connected to the output of the first and second windings of the two cores and to said alternating current source.

4. A magnetic amplifier comprising a first magnetizable core carrying a. first winding, a second magnetizable core carrying a first winding,

' an alternating current. source for energizing said windings, rectifying means for each of said windings and connecting said windings in series, a

second winding for the first core, a second winding for the second core, rectifying means for each of said second windings and connecting said second windings in series opposed relation to said first windings for energization by said alternating current source, a direct current input circuit including means carried' by each of said cores and connected in aiding relation, 8. first auxiliary winding on the first core connected to the output of the rectifying means of the first winding of the first core whereby direct current flows therethrough, a second auxiliary winding on the first core connected with the output of the rectifying means of the second winding of the first core, whereby direct current flows therethrough, a first auxiliary winding on the second core connected phase shifting device and to the cutout c1"- ine magnetizabie core carrying a win second magnetizable core carrying a 1 ing, an alternating current source for ener said windings, rectifying means for ea a windings and connecting said which relation, a second winding fog second winding for the second means for each of said seconi ecting said second windings elation to said first windings saici alternating current source iary windings for the first core, iary windings being connected the rectifying means of the iii first core and the other 01" ea .21

means oi the second win second. pair of aux y Y. core, one of the last-named being connected to the cutes means 0 1e first Winding of th the other of said last-mane being connected to the output oi means of the second wind the first pair of auxinary Ji' core being wound in op ocset iary 't' din s of the seco said an inary windings acti ability of their respective c ties with alternating current and second. windings of each of 5 current input circuit inclutiii" first core and a winding on aiding relation with the firs imp i additionally varying the pet ea cores in accordance with the 5 ing in said input circuit and (17 re (D r 0 input circuit the effect of one pair 6. A "iagnetic amplifier comprising a first magiamiable core cariying a first winiiiig, a

vg'i'ietizahle core can .ng a first Win21- ternating current source for icing gs, rectifying for of said s and. connecting s indings in series rei second winding 1' the first core, a ing "0 e econd core, rec' liying c auxilinchngs the ct ted to the catch 0 e first Winch. e of "he said last 1 a secomn c each pair of auxiliary s acting to vary the pern1eability of their ZESQSS'CJ'LVBYCGYES in accordance with the alternating current i and second windings each of said. cm s, a

slice "1 nt input circuit including a winding on the f st core and i in aid ng relation with t e ing .iOi additionally Varyin saici cores accoi'da fio'ving in said input 0 with r urrcnt new in one ch windings together with one of the input gs is CULfUlE'tEiVE upon the related core and t e effect oi the second pair of amt lt'i'y wind" the second core, a phase sh ting device connected to said alternating current source, and means electrically connected to: phase shifting device nd the oiitput of the first and. second Windings of the two cores.

GUSTAV EARTH. 

